3 edition of Space Shuttle Orbiter Thermal Protection System design and flight experience found in the catalog.
Space Shuttle Orbiter Thermal Protection System design and flight experience
by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC, Springfield, Va
Written in English
|Statement||Donald M. Curry.|
|Series||NASA technical memorandum -- 104773., NASA technical memorandum -- 104773.|
|Contributions||United States. National Aeronautics and Space Administration.|
|The Physical Object|
et thermal protection system. et hardware. et range safety system. space shuttle coordinate system; orbiter structure. forward fuselage. crew compartment. airlock. forward fuselage and cabin windows. wing. midfuselage. payload bay doors. aft fuselage. oms/rcs pods. body flap. vertical tail. orbiter passive thermal control; orbiter purge, vent. Major system requirements are that the orbiter and the two solid rocket boosters be reusable. Other features of the Shuttle: The orbiter has carried a flight crew of up to eight persons. A total of 10 persons could be carried under emergency conditions. The basic mission is 7 days in space.
The aerobrake consists of an aluminumskin and stringer structure, covered with Space Shuttle Orbiter thermal protection system tiles (FRCI 12 and LI). It is 14 feet in diameter, and has a “raked-cone” design. Other, deployable, designs were considered including gas bags (“ballutes”), nd an umbrellaa -type mechanical structure. NASA Technical Memorandum Space Shuttle Orbiter Thermal Protection System Design and Flight 1, × 1,, 22 pages; MB Shuttle Booster × ; KB Shuttle Carrier Aircraft - 3, × 2,; MB.
Description. The spectrum of coverage of the volume includes aeroheating and thermal protection for high-velocity entry flight into the Earth's atmosphere (Space Shuttle), comet-like flight very close to the sun (Solar Starprobe), and entry into the gaseous envelope . The Shuttle design specifications do not require that the Orbiter be able to manage an intact abort (i.e., make it to a runway) if a second main engine should fail. If two (or all three) main engines fail within the first five to six minutes of the flight, the Space Shuttle will land in water.
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SPACE SHUTTLE ORBITER THERMAL PROTECTION SYSTEM DESIGN AND FLIGHT EXPERIENCE Donald M. Curry NASNJohnson Space Center Houston, TX ABSTRACT The Space Shuttle Orbiter Thermal Protection System materials, design approaches associated with each material, and the operationalpedorm_ce experiencedduring fifty-five successful flights aredescribed.
The Space Shuttle Orbiter Thermal Protection System materials, design approaches associated with each material, and the operational performance experienced during fifty-five successful flights are described.
The flights to date indicate that the thermal and structural design requirements were met and that the overall performance was by: The Shuttle’s Thermal Protection System (TPS) By Dennis R. Jenkins. During the original studies of lifting-reentry vehicles during the late s and s, there had been a great debate over the relative merits of active cooling systems versus passive systems for the vehicle structure.
Space Shuttle Thermal Protection System 3 TPS requirements Orbiter structure temperature File Size: KB. Orbiter’s Thermal Protection System (TPS) resulted in unanticipated post-flight system inspections, repairs and replacements (R&R), and significan t operational expenses.
Figure : Charles Camarda. robotic arm for the inspection of the Thermal Protection System. The nose cap and wing leading edge reinforced carbon-carbon survey was scheduled for post undock af te r hO b iB o mS ns ydv u gFl D 4 extravehicular activity.
A stronau K eNyb g,ST w k h c l on the aft ﬂight deck of Space Shuttle Discovery during Flight Day 2 activities. Full text of "Aerodynamic design of the space shuttle orbiter" See other formats AERODYNAMIC DESIGN OF THE SPACE SHUTTLE ORBITER by W.E.
Bornemann Manager, Space Shuttle Aerodynamics Rockwell International Corporation Space Systems Group Lakewood Boulevard Downey, CA T.E. Surber Supervisor, Orbiter Aerodyanmics and Rockwell International Corporation Space Systems. The vehicle's configuration and entry trajectory in combination with the type of thermal protection system used define the temperature distribution on the vehicle.
The Space Shuttle features a TPS system based on the use of surface materials with a high temperature capability in combination with an underlying thermal insulation to inhibit the conduction of heat to the interior of the vehicle.
Rotary National Award for Space Achievement 21 STELLAR AWARD NOMINEES - EARLY Jeremy H. Brand of NASA Johnson Space Center - Technical excellence in thermal protection system materials and processes, and key contributions to the Orbiter Damage Assessment team.
Jimmy M. Doll, Jr. of Lockheed Martin Space Systems Company - Outstanding leadership. Design example: Space Shuttle. The Space Shuttle thermal protection system was based on the use of surface materials with a high temperature capability, in combination with an underlying thermal insulation to reduce heat conduction to the interior of the vehicle.
The heat from the aerodynamic heating was thereby radiated back into space. phase of the Shuttle design and operations process – Concept Studies – weight, cost, producibility – Concept Definition – weight, cost, producibility – Preliminary Design – detail design trades- configuration, weight, cost, producibility and operations – Critical Design – same as PD but emphasis on weight, cost, and flightFile Size: 2MB.
Thirty Years of Experience with the First Reusable Thermal Protection System Hypersonic Data - National Asset Orbiter Flight Test (OFT) Data Boundary Layer Transition DTO HYTHIRM Orbiter Vehicle Surface Geometry Scans for Future CFD Analysis Incredible Improvement in Analysis Capability Motivated by Space Shuttle Issues.
The BURAN orbiter flight was a necessary step in the space engineering progress but it has left its trace not only in this field. Born in the course of work on the BURAN project new materials, technologies, computer designing methods and equipment components find an application in far, at first sight, from Space branches of economy.
It will not deal with Shuttle orbital flight, Shuttle missions or operations. The focus will be on the main elements of the orbiter vehicle: its structure, propulsion systems, thermal protection system, avionic and communication system.
Since the Challenger catastrophe many improvements have been made on the Shuttle system, which is summarized Author: Ulrich Walter. INTRODUCTION. The thermal protection system (TPS) for the RLV must protect the structure and cryogenic fuel tanks from extremely high temperatures during launch and reentry.
To meet the requirements of an RLV, the TPS must be readily producible, lightweight, operable, and reusable with a minimum lifetime of missions.
The Space Shuttle design was remarkable. The idea of?wings in [email protected] took concrete shape in the brilliant minds of NASA engineers, and the result was the most innovative, elegant, versatile, and highly functional vehicle of its time. The shuttle was indeed an engineering marvel on many counts.
Accomplishing these feats required the design. The Space Shuttle Orbiter is the first reusable entry spacecraft built on a foundation of technology and experience gained from the (fig. One of the most critical elements to the development of this capabiltiy is the reusable thermal protection system (TPS) mounted on the aluminum structure.
this approach to the Orbiter design and. ORBITER MANUFACTURING AND ASSEMBLY The structures of the orbiter were manufactured at various companies under contract to Rockwell International's Space Transportation Systems Division, Downey, Calif.
The upper and lower forward fuselage, crew compartment, forward reaction control system and aft fuselage were manufactured at Rockwell's Space Transportation Systems Division. Each NASA space shuttle designation was composed of a prefix and suffix separated by a dash.
The prefix for operational shuttles is OV, for Orbiter Vehicle. The suffix is composed of two parts: the series and the vehicle number. Series: 0 - Non-flight ready shuttles 1 - Flight ready shuttles The vehicle number is sequentially assigned within the series, beginning with 1.
Therefore, there can never be an. The only way of establishing whether the space shuttle system worked, whether or not that year design process, the computers, the heat shield, the Author: Douglas Messier. Shuttle Operational Data Book: The information in this section is compiled and updated by the JSC Projects Office's Flight Engineering and Vehicle Management Office.
These pages are in Portable Document Format .PDF). Report of the Space Shuttle Management Independent Review Team (Kraft Report) Space Shuttle Flight Durations for the Entire.The Space Shuttle thermal protection system (TPS) is the barrier that protected the Space Shuttle Orbiter during the searing 1, °C (3, °F) heat of atmospheric reentry.A secondary goal was to protect from the heat and cold of space while in orbit.MR&D Work on Space Shuttle Repair.
Since the Columbia Space Shuttle tragedy, MR&D has been significantly involved with analysis and design, fabrication and testing efforts associated with refractory composite materials and structures designs for the thermal protection system repairs of the NASA Space Shuttle.